CN103089316B - Turbine last stage flow path - Google Patents
Turbine last stage flow path Download PDFInfo
- Publication number
- CN103089316B CN103089316B CN201210434459.3A CN201210434459A CN103089316B CN 103089316 B CN103089316 B CN 103089316B CN 201210434459 A CN201210434459 A CN 201210434459A CN 103089316 B CN103089316 B CN 103089316B
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- turbine
- final stage
- gas
- ratio
- nozzle
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- 238000006243 chemical reaction Methods 0.000 claims description 13
- 210000000867 larynx Anatomy 0.000 claims 6
- 238000005259 measurement Methods 0.000 description 14
- 239000000567 combustion gas Substances 0.000 description 8
- 239000007789 gas Substances 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 238000009792 diffusion process Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
Abstract
A gas turbine engine includes a turbine and a diffuser positioned downstream of the turbine. The turbine includes a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.
Description
Technical field
The present invention relates generally to gas-turbine unit, exactly, is related to last for optimizing the combustion gas turbine of performance
Level (last stage) stream and related diffusor entry.
Background technology
In general, combustion gas turbine is driven by the hot combustion gas stream for flowing through plurality of level.Gas turbine is sent out
Motivation can generally include the bubbler positioned at the final stage downstream of turbine.Bubbler will leave the hot combustion gas stream of final stage
Kinetic energy is converted into the potential energy using increased static pressure form.Bubbler of number of different types and the like known to possible.
Known multiple parameters can be impacted to combustion gas turbine overall performance.But, it is intended to do not considering bubbler
In the case of by the change in these parameters come improve combustion gas turbine overall performance typically result in bubbler performance reduction, and
Thus combustion gas turbine overall performance and efficiency are reduced.
Accordingly, it would be desirable to a kind of turbine last stage flow path of optimization, and consider diffusor entry profile.Last stage flow path and expansion
Scattered device inlet profiles take the overall performance that should optimize turbine and bubbler into consideration.
The content of the invention
Here of the present invention provides a kind of gas-turbine unit.The gas-turbine unit can include turbine and
It is arranged at the bubbler in the turbine downstream.The turbine can include multiple final stage blades, multiple final stage nozzles, and
The measurement of the about 0.95 or higher final stage nozzle is than (gauging ratio).
The measurement is than including the ratio between throat length and pitch.The turbine includes less than about 0.7 blade
Wheel hub entrance relative Mach number.The turbine includes about 20 or higher pressure ratio.The turbine includes about 0.4 to about
0.65 radius ratio；The radius ratio includes the hub radius from rotor to the wheel hub of final stage blade, and from the rotor to
The tip radlus of the blade tip of the final stage blade.The turbine includes greater than about zero (0) wheel hub degree of reaction；The wheel hub is anti-
Dynamic degree includes the pressure ratio of the pressure ratio and final stage of the final stage blade.The turbine includes less than about 20 degree
Non-guide angle of rotation；The non-guide angle of rotation includes the angle from throat to rear end of final stage blade.The turbine includes
Less than about one (1) angle of outlet ratio；The angle of outlet ratio includes the tip-side angle of outlet and wheel hub side outlet of final stage nozzle
Angle.The turbine includes the last stage flow path being located therein.The turbine includes circuit, and the bubbler includes diffusion
Device entrance.
The present invention further provides a kind of gas-turbine unit.The gas-turbine unit can include turbine
Final stage and be arranged at the turbine the final stage downstream bubbler.The turbine can include multiple final stage oars
Leaf, multiple final stage nozzles, the stream for passing through, and the measurement ratio of the about 0.95 or higher final stage nozzle.
The measurement is than including the ratio between throat length and pitch.The turbine includes less than about 0.7 blade
Wheel hub entrance relative Mach number, and about 20 or higher pressure ratio.The turbine includes about 0.4 to about 0.65 radius
Than, greater than about zero (0) wheel hub degree of reaction, less than about 20 degreeNon-guide angle of rotation, and/or less than about one
(1) angle of outlet ratio.
The present invention further provides a kind of gas-turbine unit.The gas-turbine unit can include turbine
Final stage and bubbler.The final stage of the turbine may include multiple final stage blades, multiple final stage nozzles, pass through
Last stage flow path, and the measurement ratio of the about 0.95 or higher final stage nozzle.The final stage of the turbine may also include
About 0.4 to about 0.65 radius ratio, greater than about zero (0) wheel hub degree of reaction (degree of hub reaction), less than about
20 degreeNon-guide angle of rotation (unguided turning angle), and/or less than about one (1) the angle of outlet
Ratio (exit angle ratio).Other kinds of operational factor can be considered in this specification.
Wherein, the measurement is than including the ratio between throat length and pitch.
Described further below, those skilled in the art is read by with reference to some accompanying drawings and appended claims
It is clearly understood that these and other features and the improvement of the present invention and corresponding patent.
Description of the drawings
Schematic diagrams of the Fig. 1 for gas-turbine unit, it is illustrated that compressor, combustor, turbine and bubbler.
Fig. 2 is the side view of some of the combustion gas turbine as described in possible in this specification.
Schematic diagrams of the Fig. 3 for a part for turbine shown in Fig. 2, it is illustrated that a pair of turbomachine injection nozzles.
Schematic diagrams of the Fig. 4 for a part for turbine shown in Fig. 2 a, it is illustrated that blade.
Fig. 5 show the nozzle measurement ratio of the nozzle span across turbine shown in Fig. 2.
Component symbol list：
| Reference number | Part | Reference number | Part |
| 10 | Gas-turbine unit | 15 | Compressor |
| 20 | Air stream | 25 | Combustor |
| 30 | The fuel stream | 35 | Burning gases stream |
| 40 | Turbine | 45 | Axle |
| 50 | Load | 55 | Bubbler |
| 60 | Pillar | 65 | Wheel hub |
| 70 | Shell | 100 | Turbine |
| 110 | The first order | 120 | First order nozzle |
| 130 | First order blade | 140 | The second level |
| 150 | Second level nozzle | 160 | Second level blade |
| 170 | Final stage | 180 | Final stage nozzle |
| 190 | Final stage blade | 192 | Wheel hub |
| 196 | Blade tip | 198 | Rotor |
| 200 | Entrance | 210 | Bubbler |
| 220 | Last stage flow path | 230 | Circuit (annulus) |
| 240 | Housing | 250 | Spray nozzle front end |
| 260 | Nozzle rear end | 270 | Nozzle suction side |
| 280 | Nozzle exit pressure side | 290 | Blade front end |
| 300 | Blade rear end | 310 | Blade suction side |
| 320 | Blade is on the pressure side | 330 | Throat |
| 340 | Non-guide angle of rotation | 350 | The angle of outlet |
| 360 | Measurement ratio | 370 | Throat length |
| 380 | Pitch |
Specific embodiment
Referring now to accompanying drawing, in the accompanying drawings, the similar component being similar to during numeral indicates each view, Fig. 1 show this explanation
The schematic diagram of the gas-turbine unit 10 that may be used in book.Gas-turbine unit 10 can include compressor 15.Compression
The compression air inlet of machine 15 stream 20.Compressed air stream 20 is transported to combustor 25 by compressor 15.Combustor 25 is by compressed air
Stream 20 is mixed with pressurized flow 30, then lights the mixture to produce burning gases stream 35.Although illustrate only one
Combustor 25, but gas-turbine unit 10 can include any amount of combustor 25.Burning gases stream 35 is subsequently transported to
Turbine 40.Burning gases stream 35 drives turbine 40, so as to produce mechanical work.The mechanical work produced in turbine 40 via
Axle 45 drives compressor 15, and the external loading 50 such as electromotor.
Gas-turbine unit 10 may also include bubbler 55.Bubbler 55 can be arranged at 40 downstream of turbine.Diffusion
Device 55 can include multiple pillars 60, and these pillars are arranged on wheel hub 65, and are wrapped up by shell 70.The diameter of shell 70 can
Extend along the direction of stream.Bubbler 55 makes burning gases stream 35 axially rotate/turn to.Other portions can be used in this specification
Part or other configurations.
Gas-turbine unit 10 can use natural gas, various types of synthesis gas, and/or other kinds of fuel.
Gas-turbine unit 10 can be the General Electric positioned at New York, United States SIKA Nai Ta (Schenectady, New York)
Any one in the provided various different gas-turbine units of company (General Electric Company), which includes
(but not limited to) 7 or 9 series heavy-duty gas-turbine units and similar gas-turbine unit.Gas-turbine unit 10 can
With different configurations, and other kinds of part can be used.This specification it is also possible to use other kinds of gas turbine and send out
Motivation.This specification also can use multiple gas-turbine units, other kinds of turbine and other kinds of simultaneously
Electric equipment.
Fig. 2 show the example of the turbine 100 as described in possible in this specification.Turbine 100 can include multiple
Level.In this example, the first order 110 has first order nozzle 120 and first order blade 130, and the second level 140 is sprayed with the second level
Mouth 150 and second level blade 160, and final stage 170 has final stage nozzle 180 and final stage blade 190.This specification can be used
Any amount of level.Final stage blade 190 can extend to blade tip 194 from wheel hub 192, and may be mounted on rotor 196.Diffusion
The entrance 200 of device 210 can be arranged at 170 downstream of final stage.In general, the diameter of bubbler 210 is along the stream for passing through
Direction increases.Last stage flow path 220 can be limited/be defined by circuit (annulus) 230, neighbouring diffusion of the circuit by turbine 100
The external shell 240 of device 210 is formed.Miscellaneous part or other configurations can be used in this specification.
Fig. 3 show a pair of final stage nozzles 180.Each nozzle 180 include front end 250, rear end 260, suction side 270 and
On the pressure side 280.Similarly, Fig. 4 show the example of final stage blade 190.Final stage blade 190 also include front end 290, rear end 300,
Suction side 310 and on the pressure side 320.Nozzle 180 and blade 190 can be arranged to the circumferential arrangement in each turbine stage.Can
With using any amount of nozzle 180 and blade 190.Nozzle 180 and blade 190 can have any size or shape.This theory
Miscellaneous part or other configurations can be used in bright book.
As set forth above, it is possible to optimize any amount of operational factor, to improve the performance of turbine and bubbler.For example,
Last stage flow path 220 can be considered.As described above, last stage flow path 220 can be defined by circuit 230, the circuit is by the outer of turbine 100
Portion's housing 240 is formed.Similarly, the entrance 200 of bubbler 210 is it is possible thereby to characteristic matching or cooperation with circuit 230, so as to
Improve the performance of bubbler.Some final stage variables can include relative Mach number (relative Mach number), pressure ratio,
Radius ratio, degree of reaction (a reaction), non-guide angle of rotation (unguided turning angle) and throat distribution model
Enclose (throat distribution ranges).It is also contemplated that its dependent variable in this specification.
For example, no matter by reducing pressure ratio, increase circuit 230 or other modes are designed to final stage 170 to obtain
To low blade wheel hub entrance relative Mach number, whole efficiency can be increased.In this example, low blade wheel hub entrance is with respect to horse
Conspicuous number is smaller than about 0.7.This relative Mach number should maintain rational wheel hub conversion and performance.Setting final stage with postponing, throat
Distribution can be directed to the inlet profiles of bubbler and be optimized.
Specifically, pressure ratio can be determined across whole turbine 100, also can be across the nozzle 180 of final stage 170 and blade
190 are determined.Integral pressure ratio can be about 20 or higher.Radius ratio can be considered from rotor 196 to the wheel hub of wheel hub 192 half
Footpath, and from rotor 196 to the tip radlus of the blade tip 194 of final stage blade 190.In this example, radius ratio can be about 0.4 and arrive
About 0.65.Wheel hub degree of reaction considers the situation of the pressure ratio relative to the pressure ratio of final stage 180 of final stage blade 190.Here reality
In example, the degree of reaction in hub side can be greater than about zero (0), to maintain the sensible load around wheel hub.Non-guide angle of rotation
Degree may be set to the rear portion of blade 190 is turned to the amount of rear end 300 from throat 330.In this example, non-guide angle of rotation can
Less than about 20 degree (20 °), so that vibrations loss (shock loss) are maintained at reasonable level.Other parameter can be the angle of outlet
Ratio 350.Angle of outlet ratio 350 may be set to the tip-side angle of outlet of final stage nozzle 180 and the ratio of the hub side angle of outlet.Here
In example, angle of outlet ratio is smaller than about one (1).Its dependent variable and parameter can be considered to obtain different matching somebody with somebody in this specification
Put.
Other parameter can be final stage nozzle 180 throat distribution, or measurement than (gauging ratio) 360.It is concrete and
Speech, as tip-side measure the ratio with hub side measurement.Measurement can be by throat length 370 and adjacent nozzles than 360
Pitch 380 between 180 is estimated to account for.Throat length 370 is that the rear end 360 to the second of first jet 180 is sprayed
The distance between suction side 270 of mouth 180.Pitch 380 can be set as the front end 250 of first jet 180 and arrive second nozzle 180
The distance between front end 250.(also can be using the distance between rear end 260 in this specification.) as shown in figure 5, this specification
In the measured value of final stage nozzle 180 gradually increase from tip-side to hub side, i.e., throat is largely opened at blade tip,
And close in wheel hub.Specifically, measurement can be greater than about 0.95 than 360, so as to formed evenly radial direction work(distribution with more
Flat diffusor entry profile.
By reducing pressure ratio or increase circuit area, therefore final stage 170 can have low blade wheel hub entrance with respect to horse
Conspicuous number.Blade throat is distributed or measurement can be subsequently configured than 360, to obtain the preferable wheel of suitable diffusor entry 200
It is wide.Specifically, throat can be largely opened at blade tip, and is closed in wheel hub.Therefore, such layout optimization whirlpool
The performance of turbine and bubbler, so as to improve systematic entirety energy.In view of measurement is less than usual, i.e., throat is opened at blade tip
Degree is less, and larger in wheel hub opening degree, therefore this configuration is probably unique.
It will be appreciated that described above only relates to some embodiments of the present invention and corresponding patent.Those skilled in the art
Without departing from the spirit and scope of the present invention the present invention can be done it is various change and modifications, the present invention spirit and model
Enclose and defined by appended claims and its equivalent.
Claims (19)
1. a kind of gas-turbine unit, including：
Turbine；
The turbine includes multiple final stage blades and multiple final stage nozzles, and the larynx section ratio of the final stage nozzle is from hub side to leaf
Sharp side gradually increases；
0.4 to 0.65 radius ratio；And
Bubbler, which is arranged at the turbine downstream.
2. gas-turbine unit according to claim 1, wherein the larynx section ratio of the final stage nozzle includes the final stage
Ratio between the pitch of the throat length of nozzle and the final stage nozzle.
3. gas-turbine unit according to claim 1, wherein the turbine includes that the blade wheel hub less than 0.7 enters
Mouth relative Mach number.
4. gas-turbine unit according to claim 1, wherein the turbine includes 20 or higher pressure ratio.
5. gas-turbine unit according to claim 1, wherein the radius ratio is included from rotor to final stage blade
The hub radius of wheel hub with from the rotor to the blade tip of the final stage blade tip radlus ratio.
6. gas-turbine unit according to claim 1, wherein the turbine includes the wheel hub reaction more than zero (0)
Degree.
7. gas-turbine unit according to claim 6, wherein the wheel hub degree of reaction includes the final stage blade
The pressure ratio of pressure ratio and the final stage nozzle.
8. gas-turbine unit according to claim 1, wherein the turbine includes drawing less than the non-of 20 degree (20 °)
Lead angle of rotation.
9. gas-turbine unit according to claim 8, wherein the non-guide angle of rotation include final stage blade from
Angle of the throat to rear end.
10. gas-turbine unit according to claim 1, wherein the turbine includes the angle of outlet less than (1)
Ratio.
11. gas-turbine units according to claim 10, wherein the angle of outlet ratio includes the leaf of final stage nozzle
Sharp side outlet angle and the ratio of the hub side angle of outlet.
12. gas-turbine units according to claim 1, wherein the turbine includes the final stage stream being located therein
Road.
13. gas-turbine units according to claim 1, wherein the turbine includes circuit, the circuit is limited
Last stage flow path, and the bubbler includes diffusor entry the neighbouring circuit.
A kind of 14. gas-turbine units, including：
The final stage of turbine；
The final stage of the turbine includes multiple final stage blades, multiple final stage nozzles, and the last stage flow path for passing through,
The larynx section ratio of the final stage nozzle gradually increases from hub side to tip-side；
0.4 to 0.65 radius ratio；And
Bubbler, which is arranged at the final stage downstream of the turbine.
15. gas-turbine units according to claim 14, wherein the larynx section ratio of the final stage nozzle includes the end
Ratio between the level throat length of nozzle and the pitch of the final stage nozzle.
16. gas-turbine units according to claim 14, wherein the turbine includes the blade wheel hub less than 0.7
Entrance relative Mach number, and 20 or higher pressure ratio.
17. gas-turbine units according to claim 14, wherein the turbine includes 0.4 to 0.65 radius
Than, the wheel hub degree of reaction more than zero (0), less than the non-guide angle of rotation of 20 degree (20 °), and/or the angle of outlet less than (1)
Ratio.
A kind of 18. gas-turbine units, including：
The final stage of turbine；
The final stage of the turbine includes multiple final stage blades, multiple final stage nozzles, and the last stage flow path for passing through,
The larynx section ratio of the final stage nozzle gradually increases from hub side to tip-side；
0.4 to 0.65 radius ratio, the wheel hub degree of reaction more than zero (0), less than the non-guide angle of rotation of 20 degree (20 °),
And/or the angle of outlet ratio less than (1)；And
Bubbler.
19. gas-turbine units according to claim 18, wherein the larynx section ratio of the final stage nozzle includes the end
Ratio between the level throat length of nozzle and the pitch of the final stage nozzle.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/288057 | 2011-11-03 | ||
| US13/288,057 US8998577B2 (en) | 2011-11-03 | 2011-11-03 | Turbine last stage flow path |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103089316A CN103089316A (en) | 2013-05-08 |
| CN103089316B true CN103089316B (en) | 2017-04-12 |
Family
ID=47172449
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210434459.3A Active CN103089316B (en) | 2011-11-03 | 2012-11-02 | Turbine last stage flow path |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US8998577B2 (en) |
| EP (1) | EP2589751B1 (en) |
| CN (1) | CN103089316B (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5999348B2 (en) * | 2012-10-31 | 2016-09-28 | 株式会社Ihi | Turbine blade |
| US10018075B2 (en) * | 2015-04-22 | 2018-07-10 | General Electric Company | Methods for positioning neighboring nozzles of a gas turbine engine |
| US20170130587A1 (en) * | 2015-11-09 | 2017-05-11 | General Electric Company | Last stage airfoil design for optimal diffuser performance |
| US20170130596A1 (en) * | 2015-11-11 | 2017-05-11 | General Electric Company | System for integrating sections of a turbine |
| JP6971564B2 (en) | 2015-12-18 | 2021-11-24 | ゼネラル・エレクトリック・カンパニイ | Turbomachinery and turbine nozzles for it |
| US9963985B2 (en) | 2015-12-18 | 2018-05-08 | General Electric Company | Turbomachine and turbine nozzle therefor |
| US9957804B2 (en) | 2015-12-18 | 2018-05-01 | General Electric Company | Turbomachine and turbine blade transfer |
| WO2017105259A1 (en) * | 2015-12-18 | 2017-06-22 | General Electric Company | Vane and corresponding turbomachine |
| US9957805B2 (en) | 2015-12-18 | 2018-05-01 | General Electric Company | Turbomachine and turbine blade therefor |
| US11280199B2 (en) | 2018-11-21 | 2022-03-22 | Honeywell International Inc. | Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution |
| US10859094B2 (en) * | 2018-11-21 | 2020-12-08 | Honeywell International Inc. | Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution |
| US11181120B2 (en) | 2018-11-21 | 2021-11-23 | Honeywell International Inc. | Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution |
| US11454195B2 (en) | 2021-02-15 | 2022-09-27 | General Electric Company | Variable pitch fans for turbomachinery engines |
| US11946437B2 (en) | 2021-02-15 | 2024-04-02 | General Electric Company | Variable pitch fans for turbomachinery engines |
| US11608754B2 (en) | 2021-07-14 | 2023-03-21 | Doosan Enerbility Co., Ltd. | Turbine nozzle assembly and gas turbine including the same |
| US11795824B2 (en) * | 2021-11-30 | 2023-10-24 | General Electric Company | Airfoil profile for a blade in a turbine engine |
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| US3475108A (en) * | 1968-02-14 | 1969-10-28 | Siemens Ag | Blade structure for turbines |
| US4080102A (en) * | 1975-05-31 | 1978-03-21 | Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft | Moving blade row of high peripheral speed for thermal axial-flow turbo machines |
| CN1243910A (en) * | 1998-07-31 | 2000-02-09 | 东芝株式会社 | High effective blade structure of turbine |
| CN1840857A (en) * | 2005-03-31 | 2006-10-04 | 株式会社日立制作所 | Axial turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4557113A (en) * | 1984-06-15 | 1985-12-10 | Westinghouse Electric Corp. | Single low pressure turbine with zoned condenser |
| JP2000204903A (en) * | 1999-01-06 | 2000-07-25 | Hitachi Ltd | Axial turbine |
| JP4184565B2 (en) * | 2000-02-10 | 2008-11-19 | 株式会社東芝 | Steam turbine nozzle and steam turbine using the steam turbine nozzle |
| JP3912989B2 (en) * | 2001-01-25 | 2007-05-09 | 三菱重工業株式会社 | gas turbine |
| US6979178B2 (en) * | 2001-06-18 | 2005-12-27 | Bharat Heavy Electricals Ltd. | Cylindrical blades for axial steam turbines |
-
2011
- 2011-11-03 US US13/288,057 patent/US8998577B2/en active Active
-
2012
- 2012-11-01 EP EP12190981.6A patent/EP2589751B1/en active Active
- 2012-11-02 CN CN201210434459.3A patent/CN103089316B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3475108A (en) * | 1968-02-14 | 1969-10-28 | Siemens Ag | Blade structure for turbines |
| US4080102A (en) * | 1975-05-31 | 1978-03-21 | Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft | Moving blade row of high peripheral speed for thermal axial-flow turbo machines |
| CN1243910A (en) * | 1998-07-31 | 2000-02-09 | 东芝株式会社 | High effective blade structure of turbine |
| CN1840857A (en) * | 2005-03-31 | 2006-10-04 | 株式会社日立制作所 | Axial turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2589751A3 (en) | 2018-03-14 |
| US8998577B2 (en) | 2015-04-07 |
| CN103089316A (en) | 2013-05-08 |
| EP2589751B1 (en) | 2019-03-27 |
| US20130115075A1 (en) | 2013-05-09 |
| EP2589751A2 (en) | 2013-05-08 |
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